Academic... deo Consider a classically configured airplane with the following parameters: weight W 120 kN wing area S-50 m area of horizontal tail S-12 m airplane lift curve slope CL -0.08/degree tail lift curve slope Cita =0.06/degree horizontal tail volume V-0.9 In two subsequent flight tests in air of density p-0.55 kg/m, the airplane is trimmed for straight, level and unaccelerated flight at different velocities. The following velocites to and associated tail incidences are recorded: Test 1 Test 2 Voo (m/s) 120 220 it (degrees) 2.5 2.0 Use this data to calculate the static margin SM Enter your answer as a decimal number (NOT in %) in the text box and upload your workings together with those of Question 1 as described in the instructions above.